WO2012003706A1 - Moteur à rotor supersonique - Google Patents

Moteur à rotor supersonique Download PDF

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Publication number
WO2012003706A1
WO2012003706A1 PCT/CN2011/000471 CN2011000471W WO2012003706A1 WO 2012003706 A1 WO2012003706 A1 WO 2012003706A1 CN 2011000471 W CN2011000471 W CN 2011000471W WO 2012003706 A1 WO2012003706 A1 WO 2012003706A1
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WO
WIPO (PCT)
Prior art keywords
supersonic
rotating structure
storage tank
combustion chamber
reducing agent
Prior art date
Application number
PCT/CN2011/000471
Other languages
English (en)
Chinese (zh)
Inventor
靳北彪
Original Assignee
Jin Beibiao
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Jin Beibiao filed Critical Jin Beibiao
Publication of WO2012003706A1 publication Critical patent/WO2012003706A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/32—Non-positive-displacement machines or engines, e.g. steam turbines with pressure velocity transformation exclusively in rotor, e.g. the rotor rotating under the influence of jets issuing from the rotor, e.g. Heron turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/18—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means
    • F01D1/22—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means traversed by the working-fluid substantially radially

Definitions

  • the present invention relates to the field of thermal energy and power, and more particularly to a supersonic rotary engine.
  • the supersonic jet channel body (such as a rocket nozzle) can be used as a thrust generating engine to convert thermal energy into supersonic gas kinetic energy with very high efficiency.
  • the supersonic jet channel body can be very High propulsion efficiency, when the supersonic jet channel body moves at a speed close to the speed of supersonic gas ejected from the supersonic jet channel, the kinetic energy of the supersonic gas can be turned into a supersonic jet channel body 100%. The sum of the kinetic energy and the energy of the supersonic jet channel body.
  • thermodynamic system is simple in structure and high in efficiency, but the supersonic injection passage body is difficult to use as an engine that outputs rotational power, because when the supersonic injection passage body rotates at a high linear speed, a large centrifugal force is generated, and now It is difficult to withstand this huge centrifugal force. If the supersonic injection passage body cannot be made to move at a high linear velocity circular motion, only a part of the kinetic energy of the gas injected from the supersonic injection passage body becomes the kinetic energy of the supersonic injection passage body and the supersonic injection passage body is externally made.
  • thermodynamic system engine
  • the supersonic jet of the supersonic jet channel body can be used to efficiently output rotational power to the outside, and an extremely simple and highly efficient engine can be manufactured. Summary of the invention
  • thermodynamic system capable of outputting rotational power with a supersonic gas injected from a supersonic injection channel body
  • the working mechanism of a thermodynamic system capable of outputting rotational power with a supersonic gas injected from a supersonic injection channel body can conclude that if the efficiency of the system is to be improved, the most important There are three ways: one is to convert the thermal energy into the supersonic gas with the highest possible efficiency; the other is to make the supersonic jet channel body (rocket nozzle, ramjet nozzle, etc.) at the highest possible line speed. Circular motion; Third, if there is no way to make the supersonic jet channel body move at a relatively high linear velocity, it is necessary to find a way to recover the kinetic energy of the high velocity gas that has left the supersonic jet channel body.
  • a supersonic rotary engine comprising a supersonic injection passage, a rotating structure and a high-pressure working medium, the supersonic injection passage being disposed on the rotating structure, a working inlet of the supersonic injection passage and the a high-pressure working medium source is connected, the jetting direction of the supersonic jet channel is generally pointed by a tangent to the rotating circumference of the rotating structure body, and the rotating structure body outputs power externally; when the supersonic rotor engine is working normally, The supersonic injection channel ejects a gas velocity greater than 2 Mach, and the static pressure of the gas jet ejected from the supersonic jet channel is equal to or less than atmospheric pressure.
  • the supersonic rotor engine further includes a passive rotating structure on which a striking transmission structure is provided, and the airflow striking by the supersonic jet channel pushes the passive rotating structure on the striking transmission structure Rotating, the passive rotating structure also outputs power to the outside.
  • the rotating structure is disposed at a periphery of the passive rotating structure
  • the passive rotating structure is disposed at a periphery of the rotating structure
  • the passive rotating structure and the rotating structure are arranged side by side.
  • a working fluid inlet of two or more of the supersonic injection passages is in communication with one of the high pressure working fluid sources.
  • the supersonic jet channel is configured as a Laval nozzle.
  • the high-pressure working fluid source is disposed on the rotating structure body or on the connecting structure of the rotating structure body or on the body of the supersonic rotor engine;
  • the high-pressure working fluid source is in communication with the supersonic jet passage via a single-channel rotary joint.
  • the striking transmission structure is configured as a flow guiding channel, and the airflow injected by the supersonic injection channel obtains additional thrust to further push the passive rotating structure body when the flow guiding channel blows out from the guiding channel The passive rotating structure rotates.
  • the high-pressure working medium source is set as a rocket combustion chamber, and the rocket combustion chamber is disposed on the rotating structure body and/or the connecting structure body of the rotating structure body, and/or the rotating structure body
  • An oxidant storage tank and a reductant storage tank are disposed on the connecting structure of the rotating structure, and the oxidant storage tank and the reducing agent storage tank are in communication with the rocket combustion chamber.
  • the high-pressure working medium source is set as a rocket combustion chamber, and the rocket combustion chamber is disposed on the rotating structure body and/or the connecting structure body of the rotating structure body, and an oxidant is disposed on the body of the supersonic rotor engine Storage tank and reducing agent storage tank;
  • the oxidant storage tank and the reductant storage tank are in communication with the rocket combustion chamber via a pre-mixer via a single-channel rotary joint, the oxidant in the oxidant storage tank and the reducing agent in the reducing agent storage tank are Burning in the rocket combustion chamber;
  • the oxidant storage tank and the reductant storage tank are in communication with the rocket combustion chamber via different passages in a two-channel rotary joint, the oxidant in the oxidant storage tank and the reducing agent in the reducing agent storage tank being The rocket combustion chamber is mixed and burned.
  • the high-pressure working medium source is set as a rocket combustion chamber, and the rocket combustion chamber is disposed on the rotating structure body and/or the connecting structure body of the rotating structure body, and an oxidant is disposed on the body of the supersonic rotor engine Storage tanks, reducing agent storage tanks and expansion agent storage tanks;
  • the oxidant storage tank, the reductant storage tank, and the expansion agent storage tank are in communication with the rocket combustion chamber via a pre-mixer via a single-channel rotary joint, the oxidant and the reducing agent in the oxidant storage tank
  • the reducing agent in the storage tank enters the rocket combustion chamber and burns;
  • the two storage tanks of the oxidant storage tank, the reducing agent storage tank and the expansion agent storage tank are connected to the rocket combustion chamber via a premixer and through one of the two-channel rotary joints, third a storage tank is communicated with the rocket combustion chamber via another passage of the two-channel rotary joint, and the oxidant in the oxidant storage tank and the reducing agent in the reducing agent storage tank enter the rocket combustion chamber and burn ;
  • the oxidant storage tank, the reductant storage tank, and the expansion agent storage tank are in communication with the rocket combustion chamber via different passages of a three-way rotary joint, the oxidant and the reducing agent in the oxidant storage tank
  • the reducing agent in the storage tank enters the rocket combustion chamber and is mixed and combusted.
  • a low speed bushing is disposed between the rotating shaft of the rotating structure and the rotating shaft support.
  • a rotating shaft of the rotating structure and a passive rotating shaft of the passive rotating structure are fitted to each other, and a stationary sleeve is disposed between the rotating shaft and the passive rotating shaft.
  • the supersonic rotor engine further includes a working fluid recovery casing, and a working fluid outlet is disposed on the working fluid recovery casing, and the supersonic injection passage and the rotating structure are disposed in the working fluid recovery casing In the structure in which the passive rotating structure is disposed, the supersonic jet passage, the rotating structure, and the passive rotating structure are disposed inside the working medium recovery casing.
  • the working medium recovery casing is configured as a condensing cooling medium recovery casing, and a condensing cooler is disposed at the condensing cooling medium recovery casing, and the condensing cooling medium recovery casing is fixedly connected to the rotating structure
  • the high-pressure working medium source is disposed on the rotating structure body, the high-pressure working medium source is set as an external combustion type high-pressure working medium generator, and a burner is disposed at the external combustion type high-pressure working substance generator The burner is heated by the external combustion type high-pressure working generator, and the working fluid outlet of the condensing cooling medium recovery casing is connected with the external combustion type high-pressure working generator, under the action of centrifugal force
  • the condensed working medium is flowed from the condensing and cooling medium recovery casing to the external combustion type high-pressure working fluid generator through the working fluid outlet, and the working medium is vaporized in the external combustion type high-pressure working substance generator A high temperature and high pressure gaseous working medium enters the supersonic jet channel.
  • the so-called supersonic jet passage of the present invention refers to all passages capable of injecting supersonic gas, that is, all injection passages that can change the thermal energy and pressure energy of the gas into the kinetic energy of the injected gas, such as a Laval nozzle, a rocket nozzle, And other shapes of passages that can jet supersonic gas, such as passages between two blades that can eject supersonic gas.
  • the rotating structure in the present invention refers to any structure that can be rotated, such as a flywheel, a rod that can be rotated, and a ring structure that can be rotated.
  • the original working medium is a high pressure entering the rocket combustion chamber.
  • the so-called turning circumference of the present invention refers to the circumference of the track formed when the rotating structure is rotated, and the circumference of the track may be the circumference of the outer track of the rotating structure, the circumference of the inner track, and the circumference of the outer track of the rotating structure and the circumference of the inner track. Any point of the track is formed by the rotation of the circumference of the track.
  • the so-called tangential line of the rotating circumference of the rotating structure body is generally pointed, including the case where the tangential line of the rotating structure body is completely accurate in the injection direction, and also includes the fact that although there is a certain degree of declination, The tangential line of the rotating circumference of the rotating structure is still the direction of the injection.
  • the tangent to the circumference of the revolution may be a tangent to the circumference of the outer track, a tangent to the circumference of the inner track, and a tangent to the circumference of the track formed by any point between the circumference of the outer track of the rotating structure and the circumference of the inner track.
  • the so-called high-pressure working medium source of the present invention refers to any system capable of providing a high-pressure gas working medium, and may be a rocket combustion chamber, a ramjet combustion chamber, a pulse combustion chamber, a high-pressure steam generator (high-pressure boiler), and the like.
  • the so-called high-pressure working fluid source in the present invention includes a high-pressure working fluid source generated in the form of external combustion, a high-pressure working fluid source generated in the form of internal combustion, and a high-pressure working fluid source generated in a mixed combustion mode, and also includes a high-pressure compressed gas source.
  • the so-called high-pressure working medium generated by the internal combustion form includes a combustion chamber and a system for supplying an oxidant and a reducing agent to the combustion chamber, and may further include a system for supplying a expanding agent to the combustion chamber, and the so-called expansion agent means not participating in the combustion chemical reaction, but
  • the working fluid which is heated or vaporized in the combustion chamber to expand the volume of the gas generated by the heat, the main function of the expansion agent is to adjust the temperature in the combustion chamber and the number of moles involved in the working medium.
  • the so-called high-pressure working fluid source produced by the external combustion mode refers to a system that generates high-temperature and high-pressure working fluid by means of external combustion.
  • the so-called high-pressure working medium produced by the co-combustion mode refers to a thermodynamic system in which all or almost all of the heat released by the combustion of the fuel is involved in the work cycle.
  • the patent relating to co-firing applied by the present inventors see the patent relating to co-firing applied by the present inventors.
  • the passive rotating structure of the present invention refers to a structure that can perform a rotational motion when receiving a high-speed gas jet ejected from the supersonic jet channel body.
  • the passive rotating structure can separately output power to the outside, and can output power to the rotating structure separately, or can be combined with the rotating structure through a reversing mechanism (such as an idler) to output power.
  • the so-called striking transmission structure in the present invention refers to a structure that can be subjected to high-speed gas striking on the passive rotating structure to rotate the passive rotating structure, and can be a leaf-like structure, a channel-like structure, etc., and the gas is in the striking transmission structure. It can flow either radially or axially.
  • the gas ejected from the supersonic jet channel The flow speed is greater than Mach 3.
  • the air velocity ejected from the supersonic jet passage is greater than 4 Mach.
  • the air velocity ejected from the supersonic jet passage is greater than 5 Mach.
  • the air velocity ejected from the supersonic jet passage is greater than 6 Mach.
  • the so-called condensing cooling medium recovery casing of the present invention refers to a working fluid recovery casing having a condensing cooling function.
  • the condensing cooler refers to a device that can cool the condensing cooling medium recovery casing.
  • the so-called burner refers to a combustion device capable of burning the heat to heat the external combustion type high-pressure working generator to vaporize the internal working medium.
  • the so-called external combustion type high-pressure working fluid generator refers to a device that heats the internal working medium by external heat to generate high-temperature and high-pressure gaseous working medium.
  • connection structure of the rotating structure in the present invention means a structure connected to the rotating structure, such as a rotating shaft, a rotating arm or a gear on a rotating structure.
  • the so-called rotating structure of the present invention directly outputs power to the rotating structure to directly output power, or indirectly through the connecting structure of the rotating structure, and the passive rotating structure is also the same.
  • the rotation direction of the rotating structure and the passive rotating structure in the present invention may be the same or different.
  • a buffer structure may be provided on a portion of the passive rotating structure that is subjected to the high-speed jet airflow striking transmission of the supersonic jet passage, and the buffer structure is designed to reduce high-speed gas.
  • the reflection acts to more efficiently transfer the kinetic energy of the high velocity gas to the passive rotating structure.
  • the so-called buffer structure of the present invention may be a multi-space structure, a rough surface structure, a mesh structure or a multi-gate structure, which enables a high-speed flying gas to stay on a surface impinging on these structures, as if two viscoelastic properties.
  • the bodies collide with each other, and the kinetic energy of the high-speed moving gas can be transmitted to the passive rotating structure more efficiently.
  • the so-called supersonic jet passage in the present invention is a supersonic jet passage because of a rotary motion.
  • the design aspect should consider the influence of centrifugal force.
  • the supersonic rotary engine disclosed in the present invention can be machined from a ceramic material.
  • the rotating structure of the present invention rotates at a high speed, so the rotating structure can be directly connected to other machines, or can be connected to a generator, or the rotating structure can be used as a rotor of a generator or a rotor of a generator. On the rotating structure.
  • the working medium recovery casing can be arranged to recover the heat and the working fluid of the supersonic injection passage exhaust gas, and at the same time, the working medium recovery casing can be evacuated to be in a low pressure or vacuum state to improve the efficiency of the engine.
  • the working fluid recovered from the working fluid recovery casing can be directly discharged, can be discharged after treatment (such as three-way catalyst, etc.), or can be re-entered into the supersonic injection channel after being heated by pressure, and can also be treated to carbon dioxide. Liquefaction is recovered.
  • the supersonic injection passage operates at a lower speed than the supersonic injection passage, so the higher the speed of the supersonic injection passage, the higher the efficiency. For this reason, the higher the rotational speed of the rotating structure in the present invention, the higher the efficiency. Since high-speed rotation produces strong centrifugal force, it is very likely that the desired speed is difficult to achieve due to limitations in the prior art and materials, so the supersonic jet channel jet (exhaust gas) still has a large kinetic energy. Therefore, a passive rotating structure is provided, and the exhaust gas injected by the supersonic injection channel of the present invention is driven against the passive rotating structure by the nearly tangential overall direction, thereby causing the passive rotating structure to rotate and output power, thereby further improving the efficiency of the engine. .
  • the principle of the invention is to use the supersonic injection channel to convert the thermal energy and pressure energy of the working medium existing in the high-pressure working medium source into the kinetic energy of the high-speed gas ejected from the supersonic injection channel with the highest possible efficiency.
  • the static pressure of the high velocity gas ejected by the supersonic jet channel is equal to the supersonic jet
  • the ambient pressure at the exit of the jet channel, the ambient pressure at the exit of the sonic jet channel can be atmospheric pressure or lower than atmospheric pressure. If it is lower than atmospheric pressure, the working fluid recovery housing must be set to recover the working fluid.
  • the vacuum is drawn so that the pressure in the working fluid recovery casing is lower than the atmospheric pressure (as if the bullet was fired from the gun, the energy in the gunpowder is converted into the kinetic energy of the bullet as efficiently as possible).
  • the supersonic jet channel body (the structure that constitutes the supersonic jet channel, such as a rocket nozzle, etc.) is subjected to a reaction force, since the supersonic jet channel is provided on the rotating structure, Therefore, the rotating structure will rotate and output power to the outside.
  • the supersonic injection passage converts the pressure energy and thermal energy of all gases into the kinetic energy of the gas and obtains the reverse thrust from the process to form the rotary motion of the rotating structure to output the power.
  • the high-speed moving gas that leaves the supersonic jet channel strikes the striking transmission structure provided on the passive rotating structure, and changes the kinetic energy of the gas into the rotational motion of the passive rotating structure and outputs the power to the external rotating body and the passive rotating structure.
  • the rotating structure and the passive rotating structure may be sealed or opened.
  • two coordinate systems can be used to observe the supersonic gas, and one is disposed on the supersonic jet channel body.
  • the coordinate system and the second is the coordinate system provided on the supersonic rotor engine body.
  • a passive rotating structure is provided to recover the kinetic energy of a gas that is still moving at a high speed in a coordinate system provided on the supersonic rotor engine body, in the process, high speed
  • the gas strikes the passive rotating structure to push the passive rotating structure to rotate and output power (as if the bullet hits the target, forcing the target to shift and work externally).
  • the relationship between the rotating structure and the passive rotating structure is completely different from the relationship between the adjacent counter-rotating blades of the conventional counter-rotating steam turbine and the gas turbine.
  • both the rotating structure and the passive rotating structure of the present invention rotate; the second is according to Newton's third law, the force received by the rotating structure in the present invention is obtained by the injection of high-pressure gas, and the structure of the passive rotating structure The rotation is obtained by the impact of high-speed gas, and the conventional steam turbine and gas turbine are obtained by the change of the pressure difference.
  • the speed of the gas ejected from the supersonic injection channel in the present invention is generally at several Mach.
  • the structure disclosed in the present invention can manufacture not only a large supersonic rotary engine but also a micro supersonic rotary engine.
  • the miniature supersonic rotary engine is much more efficient than a microturbine and has a simple structure.
  • the oxidant storage tank and the reducing agent storage tank may be rotated together with the rotating structure body, or may be rotated together with the rotating structure body to supply the oxidizing agent and the reducing agent to the high-pressure working source through the rotary joint.
  • the high-pressure working fluid source can also be set to rotate with the rotating structure or not rotate together with the rotating structure, but communicate with the supersonic jet passage through the rotary joint.
  • the oxidant, reducing agent and expansion agent can be called the original working medium.
  • the original working fluid storage tank rotates together with the rotating structure body, at least two sets of supersonic rotary engine can be set, and the supersonic rotary engine works alternately. It is also possible to add a new original working fluid; it is also possible to provide a rotary joint in this system. When the engine is rotating at a high speed, the coupling of the rotary joint is separated. When the engine is at a lower rotational speed, the coupling of the rotary joint is formed to cooperate with the supersonic jet.
  • the channel replenishes the original working fluid, so that the original working fluid can be replenished to the original working fluid when the engine is at a lower speed, without stopping, and there is no need to set a plurality of supersonic rotary engines, which is like an aerial refueling of the aircraft.
  • control of the original working fluid flow rate and the control of the rotary engine can be realized by the brush power supply control solenoid valve, or through the remote control solenoid valve.
  • control valve of the original working medium and/or the control valve disposed between the high-pressure working source and the supersonic injection channel can be controlled from the body by electromagnetic control to achieve the super Control of the sonic rotor engine.
  • the rotational speeds of the rotational structure of the rotating structural body and the passive rotating structural body are different, and in many structures, they may be fitted to each other, which may cause a pair of contacts.
  • a static bushing is provided between the shafts of the two mutually facing sets to reduce the relative rotational speed.
  • the so-called low speed bushing of the present invention refers to an isolating bushing having a rotational speed lower than that of the rotating structure.
  • the purpose of the present invention is to reduce the relative rotational speed difference between the bushings to form good lubrication conditions, increase life and reliability.
  • the rotation of the low-speed bushing can be driven by the rotating bushing (the bushing of the rotating structure or the bushing of the passive rotating structure), that is, the low-speed bushing is set to free, or the corresponding driving mechanism can be set on the low-speed bushing.
  • the low speed bushing rotates.
  • the so-called stationary bushing of the present invention refers to an isolating bushing in a static state, and the stationary bushing is disposed between the rotating shaft and the passive rotating shaft which are mutually set to rotate against each other, and the purpose thereof is to reduce the between the rotating shaft and the passive rotating shaft. Relative rotational speed difference to form good lubrication conditions, increasing life and reliability.
  • the so-called rotating shaft of the present invention refers to a rotating shaft connected to the rotating structure
  • the so-called passive rotating shaft refers to a rotating shaft connected to the passive rotating body
  • the so-called rotary joint of the present invention refers to two mutually matched coupling members, wherein the rotational speed of one coupling member is different from the rotational speed of the other coupling member, and both coupling members are provided with fluid passages, and fluid passages are provided in different coupling members. Interconnected to each other to achieve a flow of fluid from one couple to another.
  • the so-called single-channel rotary joint of the present invention refers to two mutually matched coupling members, wherein the rotational speed of one coupling member is different from the rotational speed of the other coupling member, and the two coupling members are provided with fluid passages, which are arranged in different coupling parts.
  • the fluid passages communicate with each other to achieve a flow of fluid from one couple to the other Pieces.
  • the so-called two-channel rotary joint of the present invention refers to two mutually matched coupling members, wherein the rotational speed of one coupling member is different from the rotational speed of the other coupling member, and two types of fluid passages are provided in the two coupling members, which are arranged in different pairs.
  • the same type of fluid passages of the pieces communicate with each other to realize a device in which two fluids flow from one even to the other.
  • the so-called three-channel rotary joint of the present invention refers to two mutually matched coupling members, wherein the rotational speed of one coupling member is different from the rotational speed of the other coupling member, and three types of fluid passages are provided in the two coupling members, which are arranged in different coupling parts.
  • the same type of fluid passages communicate with each other to realize a device in which three fluids flow from one coupling member to the other.
  • the invention has simple structure, low manufacturing cost and high reliability.
  • the present invention greatly improves the efficiency of existing engines.
  • Figure 1 is a schematic view of Embodiment 1 of the present invention.
  • Figure 1 is a schematic view of Embodiment 2 of the present invention.
  • Figure 3 is a schematic view of Embodiment 3 of the present invention.
  • Figure 4 is a schematic view of Embodiment 4 of the present invention.
  • Figure 5 is a schematic view of Embodiment 5 of the present invention.
  • Figure 6 is a schematic view of Embodiment 6 of the present invention.
  • Figure 7 is a schematic view of Embodiment 7 of the present invention.
  • Figure 8 is a schematic view of Embodiment 8 of the present invention.
  • Figure 9 is a schematic view of Embodiment 9 of the present invention.
  • Figure 10 is a schematic view of Embodiment 10 of the present invention.
  • Figure 11 is a schematic view of Embodiment 11 of the present invention
  • Figure 12 is a schematic view of Embodiment 12 of the present invention
  • Figure 13 is a schematic view of Embodiment 13 of the present invention.
  • FIG. 16 and Figure 17 are schematic views of an embodiment 15 of the present invention.
  • Figure 18 is a schematic illustration of an embodiment 16 of the present invention.
  • the supersonic rotary engine shown in FIG. 1 includes a supersonic injection passage 1, a rotating structure 2 and a high-pressure working source 3, and the supersonic injection passage 1 is disposed on the rotating structure 2, and the working fluid of the supersonic injection passage 1
  • the inlet 1001 is in communication with the high-pressure working source 3, and the jetting direction of the supersonic jet passage 1 is generally directed by a tangent to the circumference of the rotating structure 2, and the rotating structure 2 outputs power to the outside.
  • the air velocity ejected from the supersonic jet passage is greater than 2 Mach, and the static pressure of the jet ejected from the supersonic jet passage is equal to the atmospheric pressure.
  • the supersonic rotary engine shown in FIG. 2 differs from the first embodiment in that: the supersonic injection passage 1 is set as a Laval nozzle 102, and the supersonic rotary engine further includes a passive rotating structure 5 in a passive rotating structure. 5 is provided with a striking transmission structure 52. The jet airflow of the supersonic jet channel 1 drives the passive rotating structure 5 to the passive rotating structure 5 on the striking transmission structure 52, and the passive rotating structure 5 also outputs power to the outside.
  • the passive rotating structure 5 is disposed outside the rotating structure 2, and the working inlet 1001 of the two or more supersonic jet channels 1 is in communication with a high-pressure working source 3.
  • the passive rotating structure 5 is provided with a flow guiding passage 8 , and the jetting airflow of the supersonic jetting channel 1 is driven by the passive rotating structure 5 and then flows through the guiding channel 8 to obtain additional thrust to further promote passive rotation.
  • the structure 5 is rotated.
  • the air velocity ejected from the supersonic jet passage is greater than 3 Mach.
  • the supersonic rotor engine shown in FIG. 3 differs from the second embodiment in that: the rotating structure 2 is disposed at the periphery of the passive rotating structure 5, and the supersonic jet passage 1 of the passive rotating structure 5 is An air cushion cushioning structure 51 is provided at a portion of the high-speed jet stream striking, and the air cushion cushioning structure 51 reduces reflection of the high-speed jet stream.
  • the air velocity ejected from the supersonic jet channel is greater than Mach 4.
  • the supersonic rotary engine shown in FIG. 4 differs from the second embodiment in that: the high-pressure working fluid source 3 is set as a rocket combustion chamber 31, and the rocket combustion chamber 31 is disposed on the rotating structural body 2, and is passively rotated.
  • the structure 5 and the rotating structure 2 are arranged side by side. When the supersonic rotor engine is operating normally, the air velocity ejected from the supersonic jet channel is greater than Mach 5.
  • the supersonic rotary engine shown in FIG. 5 differs from the first embodiment in that: the high-pressure working fluid source 3 is disposed on the body of the supersonic rotary engine, and the high-pressure working fluid source 3 passes through the rotary joint 10 and the supersonic jet passage 1 Connected.
  • the air velocity ejected from the supersonic jet channel is greater than Mach 6.
  • the supersonic rotary engine shown in FIG. 6 differs from the first embodiment in that it further comprises a suspension bearing 6, the suspension bearing 6 suspending the rotating structure 2, and the high-pressure working source 3 is disposed on the rotating structure 2, the high voltage
  • the working fluid source 3 is in communication with the supersonic injection passage 1, and the high-pressure working fluid source 3 is set as a rocket combustion chamber 31, and the rocket combustion chamber 31 is disposed on the rotating structural body 2, and is rotated on the rotating structural body 2
  • the connecting structure of the structural body 2 is provided with an oxidizing agent storage tank 2001 and/or a reducing agent storage tank 2002, and the oxidizing agent storage tank 2001 and the reducing agent storage tank 2002 are in communication with the rocket combustion chamber 31.
  • the supersonic rotary engine shown in FIG. 7 differs from the first embodiment in that: the high-pressure working fluid source 3 is set as the rocket combustion chamber 31, and the rocket combustion chamber 31 is provided in the rotating structural body 2 and/or the rotating structural body 2.
  • an oxidant storage tank 2001 and a reducing agent storage tank 2002 are arranged on the body of the supersonic rotary engine; the oxidant storage tank 2001 and the reducing agent storage tank 2002 are burned by the premixer 2004 through the single-channel rotary joint 10 and the rocket.
  • the chamber 31 is in communication, and the oxidant in the oxidant storage tank 2001 and the reducing agent in the reducing agent storage tank 2002 are combusted in the rocket combustion chamber 31.
  • Example 8 The supersonic rotary engine shown in Fig. 8 differs from the embodiment 7 in that the oxidant storage tank 2001 and the reductant storage tank 2002 are in communication with the rocket combustion chamber 31 via different passages in the two-way rotary joint 20, the oxidant storage tank The reducing agent in the oxidant and reductant storage tank 2002 in 2001 is mixed and burned in the rocket combustion chamber 31.
  • the supersonic rotary engine shown in FIG. 9 differs from the first embodiment in that: the high-pressure working fluid source 3 is set as the rocket combustion chamber 31, and the rocket combustion chamber 31 is provided in the rotating structural body 2 and/or the rotating structural body 2.
  • an oxidant storage tank 2001, a reducing agent storage tank 2002 and an expansion agent storage tank 2003 are arranged on the body of the supersonic rotary engine; the oxidant storage tank 2001, the reducing agent storage tank 2002 and the expansion agent storage tank 2003 are premixed.
  • the device 2004 is in communication with the rocket combustion chamber 31 via a single-channel rotary joint 10, and the oxidant in the oxidant storage tank 2001 and the reducing agent in the reducing agent storage tank 2002 enter the rocket combustion chamber 31 and combust.
  • the supersonic rotary engine shown in FIG. 10 differs from the embodiment 9 in that: two types of storage tanks in the oxidant storage tank 2001, the reducing agent storage tank 2002, and the expansion agent storage tank 2003 are re-mixed by the premixer 2004.
  • One of the passage rotary joints 20 is in communication with the rocket combustion chamber 31, and the third storage tank is connected to the rocket combustion chamber 31 via the other of the two-way rotary joints 20.
  • the oxidant and reducing agent are stored in the oxidant storage tank 2001.
  • the reducing agent in the canister 2002 enters the rocket combustion chamber 31 and burns.
  • the supersonic rotary engine shown in FIG. 11 differs from the embodiment 9 in that the oxidant storage tank 2001, the reducing agent storage tank 2002, and the expansion agent storage tank 2003 pass through different passages of the three-way rotary joint 30 and the rocket combustion chamber. 31 is connected, the oxidant in the oxidant storage tank 2001 and the reducing agent in the reducing agent storage tank 2002 enter the rocket combustion chamber 31 and are mixed and burned.
  • the supersonic rotary engine shown in Fig. 12 differs from the first embodiment in that a low speed bushing 203 is provided between the rotary shaft 200 of the rotary structural body 2 and the rotary shaft support 201.
  • the supersonic rotor engine shown in FIG. 13 differs from the first embodiment in that: the rotating shaft 200 of the rotating structural body 2 and the passive rotating shaft 500 of the passive rotating structural body 5 are set to each other, A stationary bushing 204 is disposed between the rotating shaft 200 and the passive rotating shaft 500.
  • the supersonic rotary engine shown in FIG. 14 or FIG. 15 differs from the first embodiment in that: the supersonic rotary engine further includes a working fluid recovery casing 4, and a working medium guide is disposed on the working fluid recovery casing 4.
  • the outlet 401, the supersonic injection passage 1 and the rotating structure 2 are disposed inside the working fluid recovery casing 4, and the static pressure of the airflow ejected from the supersonic injection passage is less than atmospheric pressure.
  • the supersonic injection passage 1, the rotating structure 2, and the passive rotating structure 5 are disposed inside the working medium recovery casing 4.
  • the supersonic rotary engine shown in FIG. 16 or FIG. 17 differs from the second embodiment in that: the supersonic rotary engine further includes a working fluid recovery casing 4, and a working medium is disposed on the working fluid recovery casing 4.
  • the outlet 401, the supersonic injection passage 1, the rotating structure 2 and the passive rotating structure 5 are disposed inside the working fluid recovery casing 4, and the working fluid recovery casing 4 is set as a condensing and cooling worker
  • the recovery casing 440 is provided with a condensing cooler 4401 at the condensing cooling medium recovery casing 440.
  • the condensing cooling medium recovery casing 440 is fixedly connected to the rotating structure 2, and the high-pressure working source 3 is disposed on the rotating structure 2.
  • the high-pressure working medium source 3 is set as an external combustion type high-pressure working medium generator 3331, and the external combustion type high-pressure working medium generator 3331 is provided with a burner 3332, and the burner 3332 is heated by the external combustion type high-pressure working medium 3331, and the condensing and cooling worker
  • the working fluid outlet 401 of the recovery casing 440 is in communication with the external combustion type high-pressure working generator 3331, and the condensed working medium is discharged from the condensing and cooling medium recovery casing 440 through the working fluid outlet 401 by the centrifugal force.
  • Combustion Pressure working fluid generator 3331, the external combustion type high-pressure working fluid generator 3331 working fluid is vaporized into high temperature and high pressure gaseous working channel 1 into the supersonic jet.
  • the supersonic rotary engine shown in FIG. 18 differs from the embodiment 15 in that a condensing cooler 4401 is provided at the working fluid recovery casing 4, and is disposed at the working fluid outlet 401 of the working fluid recovery casing 4.
  • Compressed gas structure 4000, high-pressure working medium source 3 is set as external combustion type high-pressure working medium generator 3331
  • burner 3332 is installed in external combustion type high-pressure working medium generator 3331
  • burner 3332 is heated by external combustion type high-pressure working medium generator 3331.
  • the working fluid outlet 401 of the working fluid recovery casing 4 is connected to the external combustion type high-pressure working generator 3331 via the compressed air structure 4000, and the working medium in the external combustion type high-pressure working generator 3331 is set to helium, in the external combustion type.
  • the helium gas in the high-pressure working medium generator 3331 is heated into a high-temperature high-pressure helium gas, and the high-temperature high-pressure helium gas is sprayed through the supersonic jet channel 1 and the passive rotating structure 5 is rotated into a working medium to recover the working medium.
  • the casing 4 is cooled and pressurized by the compressed air structure 4000 in the working medium recovery casing 4, and then enters the external combustion type high-pressure working generator 3331 to enter the next cycle; the so-called gas pressure structure is set A blade pressurization structure on the rotating structure 2 or on the passive rotating structure 5.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

L'invention concerne un moteur à rotor supersonique comprenant un canal de jet supersonique (1), un corps à structure rotative (2) et une source de fluide de travail haute pression (3). Le canal de jet supersonique (1) est disposé sur le corps à structure rotative (2). L'orifice d'entrée de fluide de travail (1001) du canal de jet supersonique (1) communique avec la source de fluide de travail haute pression (3). Le canal de jet supersonique (1) utilise la direction tangentielle de la circonférence rotative du corps à structure rotative (2) comme direction de jet. Le corps à structure rotative (2) émet en sortie une puissance. Le moteur selon l'invention présente une structure simple, un coût de fabrication réduit et une fiabilité élevée, ainsi qu'une efficacité considérablement accrue.
PCT/CN2011/000471 2010-07-07 2011-03-21 Moteur à rotor supersonique WO2012003706A1 (fr)

Applications Claiming Priority (12)

Application Number Priority Date Filing Date Title
CN201010219461.X 2010-07-07
CN201010219461 2010-07-07
CN201010234776 2010-07-23
CN201010234776.1 2010-07-23
CN201010243570 2010-08-03
CN201010243570.5 2010-08-03
CN201010257437.5 2010-08-19
CN201010257437 2010-08-19
CN201010278072.4 2010-09-10
CN201010278072 2010-09-10
CN201010501107.6 2010-10-09
CN201010501107 2010-10-09

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WO2012003706A1 true WO2012003706A1 (fr) 2012-01-12

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WO (1) WO2012003706A1 (fr)

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EP3161217A4 (fr) * 2014-06-30 2018-04-04 Robert Kremer Appareil, système et procédé pour utiliser une énergie thermique
CN109139292A (zh) * 2018-09-12 2019-01-04 安徽工业大学 一种旋转喷气转子
US10184229B2 (en) 2010-07-30 2019-01-22 Robert Kremer Apparatus, system and method for utilizing thermal energy
US11988173B2 (en) 2020-10-21 2024-05-21 Raytheon Company Multi-pulse propulsion system with passive initiation

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CN103573471A (zh) * 2012-10-08 2014-02-12 摩尔动力(北京)技术股份有限公司 预增压旋转冲压发动机
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CN103590919A (zh) * 2012-10-22 2014-02-19 摩尔动力(北京)技术股份有限公司 高压喷气推进转子发动机
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CN103775244B (zh) * 2013-01-18 2016-03-30 摩尔动力(北京)技术股份有限公司 喷射双流转子发动机
CN103899418A (zh) * 2013-02-18 2014-07-02 摩尔动力(北京)技术股份有限公司 遥供转子发动机
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CN103982298A (zh) * 2013-05-11 2014-08-13 摩尔动力(北京)技术股份有限公司 内燃气体液化物高温发动机
CN103982616A (zh) * 2013-05-12 2014-08-13 摩尔动力(北京)技术股份有限公司 液压转子变速机构
CN104265504B (zh) * 2013-08-07 2016-08-24 摩尔动力(北京)技术股份有限公司 转燃发动机
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CN104265505B (zh) * 2013-09-13 2016-08-24 摩尔动力(北京)技术股份有限公司 公转流道发动机
CN107061103A (zh) * 2017-06-16 2017-08-18 传孚科技（厦门）有限公司 液压能量转换装置
CN112211724A (zh) * 2020-10-14 2021-01-12 赵呈印 一种发动机及飞行器

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US10184229B2 (en) 2010-07-30 2019-01-22 Robert Kremer Apparatus, system and method for utilizing thermal energy
EP3161217A4 (fr) * 2014-06-30 2018-04-04 Robert Kremer Appareil, système et procédé pour utiliser une énergie thermique
CN109139292A (zh) * 2018-09-12 2019-01-04 安徽工业大学 一种旋转喷气转子
US11988173B2 (en) 2020-10-21 2024-05-21 Raytheon Company Multi-pulse propulsion system with passive initiation

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